带副翼偏转的三角翼自由滚转运动数值模拟

doi:CNKI:11-1929/V.20111125.1301.001

流体力学与飞行力学

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带副翼偏转的三角翼自由滚转运动数值模拟

李喜乐, 杨永

西北工业大学翼型叶栅空气动力学国家重点实验室, 陕西西安 710072

收稿日期:2011-05-13 修回日期:2011-07-10 出版日期:2012-03-25 发布日期:2012-03-24
通讯作者: 杨永 E-mail:yyang@nwpu.edu.cn

Numerical Simulation of the Free Rolling Motion of a Delta Wing Configuration with Aileron Deflection

LI Xile, YANG Yong

National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China

Received:2011-05-13 Revised:2011-07-10 Online:2012-03-25 Published:2012-03-24

摘要/Abstract

摘要： 通过耦合求解非定常Euler/Navier-Stokes方程和单自由度滚转运动方程,对带副翼偏转的65°后掠角尖前缘三角翼WI1-SLE自由滚转运动进行了研究,Navier-Stokes方程的求解采用基于Spalart-Allmaras湍流模型的脱体涡模拟(DES)。在多块结构网格上,应用基于弧长的无限插值理论(TFI)生成变形网格,实现副翼偏转,而三角翼的滚转运动则通过网格的整体旋转实现。结果表明:Euler方程和DES方法均准确地模拟出了三角翼在滚转运动过程中存在的3个平衡位置。出现平衡位置的原因分别是:①流动对称性;②机翼左侧发生涡破裂的分离涡与右侧分离涡相互平衡使得滚转力矩为0,并且平衡位置仅与三角翼两侧涡强的差有关;③副翼偏转和左右机翼不对称分离涡涡强差产生的滚转力矩相互平衡。此外,滚转运动对副翼偏角幅值很敏感,幅值的微小改变会影响最终的平衡位置和向平衡位置运动的路径。

关键词: 三角翼, 脱体涡模拟, 欧拉方程, 副翼偏转, 自由滚转运动, 网格变形, 涡破裂

Abstract: To study the free rolling movement of a 65? swept sharp leading edge delta wing with aileron deflection, unsteady Euler/Navier-Stokes equations are solved synchronously with the free rolling motion equation of a rigid body. Navier-Stokes simulations are conducted adopting the detached-eddy simulation (DES) based on an Spalart-Allmaras model. In the context of a multiblock structured grid, the arc-length based transfinite interpolation (TFI) method is employed to realize the aileron deflection, while the rolling of the wing is achieved by rotating the whole grid. The analysis of the responses of free-to-roll movement due to the scheduled aileron deflections shows that this delta wing has three different equilibrium positions during rolling which couple well between the two approaches. The wing at the three equilibrium locations are (1) due to symmetric flow, (2) characterized by vortex breakdown on the portside and separated vortex on the starboard side of the wing and dominated by their vortex strength difference, (3) resulting from the rolling moment balance between the contributions from the aileron deflection and leading edge vortices. Additionally, the rolling motion of the delta wing is very sensitive to the amplitude of the aileron deflection angle, which influences the final equilibrium position and the path to it.

Key words: delta wing, detached-eddy simulation, Euler equation, aileron deflection, free rolling motion, mesh deforming, vortex breakdown

中图分类号:

V211.3

李喜乐, 杨永. 带副翼偏转的三角翼自由滚转运动数值模拟[J]. 航空学报, 2012, (3): 453-462.

LI Xile, YANG Yong. Numerical Simulation of the Free Rolling Motion of a Delta Wing Configuration with Aileron Deflection[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (3): 453-462.

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E-mail：hkxb@buaa.edu.cn

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带副翼偏转的三角翼自由滚转运动数值模拟

Numerical Simulation of the Free Rolling Motion of a Delta Wing Configuration with Aileron Deflection

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